Data obtained at various frequencies and amplitudes for angles of attack from 0 to about 32° using oscillatory technique; static lateral and longitudinal stability data obtained at Mach number of 0.13 and Reynolds number of about 0.83×106.
Effects of fuselage nose length and canopy on low-speed oscillatory yawing derivatives of swept-wing airplane model with fuselage of circular cross section
NASA -- Memo
National Aeronautics and Space Administration -- Memorandums ; Memo n 1-15-59L
1959
28 pages
Report
English
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